Abstract: An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Abstract: A space vehicle system, a method of manufacturing a multiple space vehicle system, and a method of disposing space vehicles into Earth orbit are disclosed. The space vehicle system may include a first space vehicle including a first core structure with a first wall thickness. The space vehicle system may include a second space vehicle including a second core structure with a second wall thickness, the second wall thickness different from the first wall thickness, and the second core structure releasably attached to the first space vehicle in a stacked configuration.

Abstract: A space vehicle system, a method of manufacturing a multiple space vehicle launch system, and a method to transmit a launch load between space vehicles during a launch are disclosed. The space vehicle system may include a first space vehicle including a first core structure, a second space vehicle including a second core structure releasably attached to the first space vehicle in a stacked configuration, a first solar array supported by the first core structure, the first core structure extending beyond a lower edge of the first solar array, and a second solar array supported by the second core structure, the second core structure extending beyond an upper edge of the second solar array.

Abstract: An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Abstract: An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Abstract: An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Abstract: A satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell.

Abstract: A carbon nanotube enhanced polymer includes a polymer and a plurality of carbon nanotube sheetlets mixed with the polymer. The carbon nanotube sheetlets each include a network of intertwined carbon nanotubes.

Abstract: A sealant containment assembly for enclosing fasteners disposed within a confined space. The sealant containment assembly includes a first containment member and a second containment member that extend between two surfaces. The first and second containment members each include structure-engaging ends for engaging a structural member and the first and second containment members each include enclosure ends that connect the first and second containment members together to enclose the fasteners within a confined space defined by the first and second containment members, the first and second surfaces, the structural member and the connected enclosure ends. The assembly also includes at least one injection port disposed outside of the confined space but is in communication with at least one distribution port disposed inside the confined space for filling the confined space with sealant, thereby embedding the fasteners in sealant.

Abstract: A space vehicle system, a method of manufacturing a multiple space vehicle launch system, and a method to transmit a launch load between space vehicles during a launch are disclosed. The space vehicle system may include a first space vehicle including a first core structure, a second space vehicle including a second core structure releasably attached to the first space vehicle in a stacked configuration, a first solar array supported by the first core structure, the first core structure extending beyond a lower edge of the first solar array, and a second solar array supported by the second core structure, the second core structure extending beyond an upper edge of the second solar array.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

Abstract: This disclosure provides a cap assembly for encapsulating a fastener or portion of a fastener that protrudes from a surface and into a confined space. The cap assembly includes a plurality of nested sections that telescope a collapsed configuration to an extended configuration. The plurality of nested sections includes a base section that includes a base rim that engages the surface in the extended configuration. The plurality of nested sections also includes an end section that has an end wall. The end wall and the base rim define a length of the cap assembly in the extended configuration that is sufficient to encapsulate the fastener within the cap assembly with the base rim engaging the surface and the end wall spaced apart from a distal end of the fastener.

Abstract: A sealant containment assembly for enclosing fasteners disposed within a confined space. The sealant containment assembly includes a first containment member and a second containment member that extend between two surfaces. The first and second containment members each include structure-engaging ends for engaging a structural member and the first and second containment members each include enclosure ends that connect the first and second containment members together to enclose the fasteners within a confined space defined by the first and second containment members, the first and second surfaces, the structural member and the connected enclosure ends. The assembly also includes at least one injection port disposed outside of the confined space but is in communication with at least one distribution port disposed inside the confined space for filling the confined space with sealant, thereby embedding the fasteners in sealant.

Abstract: This disclosure provides a cap assembly for encapsulating a fastener or portion of a fastener that protrudes from a surface and into a confined space. The cap assembly includes a plurality of nested sections that telescope a collapsed configuration to an extended configuration. The plurality of nested sections includes a base section that includes a base rim that engages the surface in the extended configuration. The plurality of nested sections also includes an end section that has an end wall. The end wall and the base rim define a length of the cap assembly in the extended configuration that is sufficient to encapsulate the fastener within the cap assembly with the base rim engaging the surface and the end wall spaced apart from a distal end of the fastener.

Abstract: A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing is disclosed. The vehicle launch system may include a first space vehicle including a first core structure and a second space vehicle including a second core structure. The second core structure may be oriented relative to the first space vehicle such that when placed within a fairing, a launch load is transmitted from the first core structure of the first space vehicle and is borne by the second core structure of the second space vehicle. The first space vehicle and the second space vehicle each include respective propulsion units.

Abstract: A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

Abstract: A spacecraft may include an upper core structure or a lower core structure. The upper core structure may include an upper cylinder for supporting an upper spacecraft of a dual-manifest launch configuration. The lower core structure may include a lower cylinder for supporting a lower spacecraft with the upper cylinder mounted on top of the lower cylinder. The upper cylinder may have an upper cylinder inner diameter that may be substantially similar to the lower cylinder inner diameter.

Abstract: A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring.

Abstract: A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing is disclosed. The vehicle launch system may include a first space vehicle including a first core structure and a second space vehicle including a second core structure. The second core structure may be oriented relative to the first space vehicle such that when placed within a fairing, a launch load is transmitted from the first core structure of the first space vehicle and is borne by the second core structure of the second space vehicle. The first space vehicle and the second space vehicle each include respective propulsion units.